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Publication numberCN101900077 A
Publication typeApplication
Application numberCN 201010197617
Publication date1 Dec 2010
Filing date28 May 2010
Priority date28 May 2009
Also published asCN101900077B, EP2275672A2, EP2275672A3, EP2275672B1, US7857597, US20100143144
Publication number201010197617.9, CN 101900077 A, CN 101900077A, CN 201010197617, CN-A-101900077, CN101900077 A, CN101900077A, CN201010197617, CN201010197617.9
InventorsEVsj安居里, S赫尔, TK维姆里
Applicant通用电气公司
Export CitationBiBTeX, EndNote, RefMan
External Links: SIPO, Espacenet
Boundary layer fins for wind turbine blade
CN 101900077 A
Abstract
The invention relates to a boundary layer fins for wind turbine blade. Concretely a wind turbine blade includes a plurality of boundary layer fins, aligned substantially parallel to a direction of flow over the blade, for reducing boundary layer separation from the blade.
Claims(10)  translated from Chinese
  1. 一种风力涡轮机叶片,包括多个边界层翅片,所述边界层翅片大致平行于所述叶片上的流动方向对准,以便减小边界层与所述叶片的分离。 A wind turbine blade, the boundary layer comprising a plurality of fins, the fin is substantially parallel to the boundary layer flow direction of the blade is aligned so as to reduce boundary layer separation and the blade.
  2. 2.根据权利要求1所述的风力涡轮机叶片,其特征在于,各所述边界层翅片所具有的高度处在对应边界层翅片处的局部边界层厚度的大约25%至100%之间。 The wind turbine blade according to claim 1, characterized in that, between about 25 to 100% of the local boundary layer thickness corresponding to each of the boundary layer at the fin has a fin height of the boundary layer at the .
  3. 3.根据权利要求1所述的风力涡轮机叶片,其特征在于,各所述边界层翅片的顶面所具有的曲率半径处在对应边界层翅片处的局部边界层厚度的大约2至15倍之间。 3. The wind turbine blade according to claim 1, characterized in that the radius of curvature of the top surface of each of said fins has a boundary layer in the local boundary layer thickness of the fin at the boundary corresponding to approximately 2 to 15 between times.
  4. 4.根据权利要求1所述的风力涡轮机叶片,其特征在于,各所述边界层翅片的顶面所具有的曲率半径处在大约40毫米至150毫米之间。 4. The wind turbine blade according to claim 1, characterized in that the radius of curvature of the top surface of each of said fins has a boundary layer at between about 40 to 150 mm.
  5. 5.根据权利要求1所述的风力涡轮机叶片,其特征在于,各所述边界层翅片所具有的长度处在对应边界层翅片高度的大约2至40倍之间。 5. The wind turbine blade according to claim 1, characterized in that, between about 2-40 times the fin height corresponding to the boundary layer of the boundary layer of each of the fins having a length at.
  6. 6. 一种用于风力涡轮机的叶片,包括:多个边界层翅片,各翅片均大致沿翼弦方向在所述叶片的吸入表面上对准,以便减小边界层与所述叶片的分离;各所述边界层翅片均布置在所述叶片的翼展的外部50%至90%之间;以及各所述边界层翅片的前缘均布置在距所述叶片的前缘为对应翼弦的大约15%至90% 之间。 A blade for a wind turbine, comprising: a plurality of boundary fins, the fins are substantially chordwise direction on the suction surface of the blade is aligned with the blade so as to reduce the boundary layer separated; each of the boundary layer between the fins are disposed outside the blade span of 50 to 90%; and each of the boundary layer are arranged at the leading edge of the fin from the leading edge of the blade is the corresponding chord between about 15-90%.
  7. 7.根据权利要求6所述的风力涡轮机叶片,其特征在于,各所述边界层翅片的前缘均布置在距所述叶片的前缘为对应翼弦的50%至90%之间。 7. The wind turbine blade according to claim 6, characterized in that each of said boundary layer are arranged at the leading edge of the fin from the leading edge of the blade is between 50-90% of the corresponding chord.
  8. 8.根据权利要求7所述的风力涡轮机叶片,其特征在于,各边界层翅片的长度均处在对应边界层翅片高度的大约2至40倍之间。 8. The wind turbine blade according to claim 7, characterized in that the average length of each fin in the boundary layer between the fin height corresponding to the boundary layer of approximately 2 to 40 times.
  9. 9.根据权利要求7所述的风力涡轮机叶片,其特征在于,各所述边界层翅片的顶面所具有的曲率半径均处在对应边界层翅片高度的大约2至60倍之间。 9. The wind turbine blade according to claim 7, characterized in that the radius of curvature of the top surface of each of the boundary layer has the fins are at the boundary layer between the fin height corresponding to approximately 2 to 60 times.
  10. 10.根据权利要求7所述的风力涡轮机叶片,其特征在于,各所述边界层翅片的厚度均处在对应边界层翅片高度的大约10%至100%之间。 10. The wind turbine blade according to claim 7, characterized in that the boundary layer thickness of each fin are at the boundary layer between the fin height corresponding to about 10 to 100%.
Description  translated from Chinese

用于风力涡轮机叶片的边界层翅片 Boundary fins for a wind turbine blade

技术领域 Technical Field

[0001 ] 本文所述的主题主要涉及风力涡轮机叶片,并且更具体地涉及用于风力涡轮机叶片的边界层翅片(fin)。 Relating to [0001] as described herein primarily relates to wind turbine blades, and more particularly relates to a blade for a wind turbine boundary layer fin (fin).

背景技术 Background

[0002] 风力涡轮机是一种用于将风中的动能转变成机械能的机器。 [0002] The wind turbine is a machine for converting the kinetic energy in wind into mechanical energy. 如果机械能由机械直接使用,如用来抽水或磨麦,则风力涡轮机可称为风车。 If the mechanical energy is used directly by machinery, such as to pump water or to grind wheat, then the wind turbine may be referred to as a windmill. 类似的是,如果机械能转变成电力, 则机器还可称为风力发电机或风力发电设备。 Similarly, if the mechanical energy is converted to electricity, then the machine may also be referred to as a wind generator or wind power plant.

[0003] 风力涡轮机通常根据叶片旋转所围绕的垂直轴线或水平轴线来分类。 [0003] Wind turbines are typically categorized according to the vertical or horizontal axis about which the blades rotate classified. 一种所谓的水平轴式风力发电机在图1中示意性地示出,且可从通用电气公司获得。 A so-called horizontal-axis wind generator is schematically illustrated in Figure 1, and can be obtained from the General Electric Company. 用于风力涡轮机2的该特定构造包括支承机舱6的塔架4,该机舱6包含传动系8。 This particular configuration for a wind turbine 2 includes a tower 4 supporting a nacelle 6, which contains the drive train 8 nacelle 6. 叶片10布置在"自旋体(spinner) 〃或桨毂9上,以便在传动系8的一端于机舱6外形成"转子"。旋转叶片10驱动齿轮箱12,该齿轮箱12在传动系8的另一端处连接到发电机14上,传动系8连同控制系统16 —起布置在机舱6内,该控制系统16可接收来自于风速计18的输入。 Blades 10 are arranged in the "spinner (spinner) 〃 or hub 9 to 8 at one end of the drive train is formed in the outer cabin 6" rotor. "10 drives rotary blades gear box 12, the gear box 12 in the drive train 8 The other end is connected to the generator 14, the drive train control systems along with 8 16-- from 6 disposed in the cabin, the control system 16 may receive input from the anemometer 18.

[0004] 当叶片10在"转子平面"内自旋时,该叶片产生升力且从流动空气中俘获随后给予转子的动量。 [0004] When the blade 10 spins in a "rotor plane," the blade to generate lift and capture momentum from then to the rotor of the air flow. 各叶片10通常均在其"根部"端处固定到桨毂9上,且然后沿径向"向外侧"“翼展"至自由的"末梢"端。 Each blade 10 is typically at its "root" end is fixed to the hub 9, and then radially "outwardly" "span" to a free, "tip" end. 叶片10的前部或"前缘"连接首先接触空气的叶片最前点。 Most points front, or "leading edge" of the blade 10 is connected first contact the air blades. 叶片10的后部或"后缘"为已由前缘所分离的空气流在经过叶片的吸入表面和压力表面之后重新结合的部位。 Rear or "trailing edge," of the blade 10 is separated by the leading edge of the air stream in the suction surface of the blade after the pressure surface and re-binding site. “弦线"连接叶片前缘和后缘中心。 A "chord line" connecting the center of the blade leading and trailing edges. 弦线的长度简称为"翼弦"。 The length of the chord line referred to as "chord." 叶片10的厚度可在沿翼展变化,而用语"厚度"通常用于描述任何特定弦线在叶片相对侧上的低压吸入表面与高压表面之间的最大距离。 The thickness of the blade 10 may change along the span, and the term "thickness" is typically used to describe any particular chord line on the opposite side of the blade of the low pressure suction surface and the maximum distance between the high-pressure surface.

[0005]“边界层"为减速空气区,其紧邻运动叶片10的表面。 [0005] "boundary layer" of air is the deceleration zone, the movement of the blade 10 close to the surface. 边界层的厚度通常限定为距叶片在其处流动速度为"自由流"速度的99%的距离,在该处,空气不受叶片粘滞力或摩擦力的影响,但感觉到势流超过边界层。 The thickness of the boundary layer from the blade is generally defined as the flow rate at which the 99% "free flow" speed of the distance, where, without force or effect blade viscous friction of air in, but feel the potential flow over the border layer. 当边界层传送得过远而足以克服相反的压力梯度时,就会出现"流动分离",流动速度下降至几乎为零。 When the boundary layer is sufficient to overcome the transmission too far and opposite pressure gradient, there will be "flow separation", the flow speed is reduced to almost zero. 流体流然后因流过叶片10而变得分离,且作为替代而形成涡旋和涡流。 Fluid then flows through the blade 10 due to become separated, and as an alternative to the formation of vortex and vortex.

[0006] 这种边界层分离可增大叶片10上的阻力(drag),尤其是"压力阻力",这是在物体穿过流体时由物体前表面与后表面之间的压差造成的。 [0006] This boundary layer separation can increase the resistance (drag) on the blade 10, especially the "pressure resistance", which is when an object passes through the front surface of the fluid by the pressure difference between the rear surface of the object caused. 边界层分离还可导致失速和涡流泄出,这可造成噪音和叶片10中的结构振动。 Boundary layer separation can also lead to stalling and eddy escape, which can result in structural vibration noise and the blade 10. 为此,在空气动力表面的设计中已经进行了很多努力和研究,这些空气动力表面延迟流动分离和保持局部流尽可能久地附着在叶片10 上。 For this reason, the design of the aerodynamic surfaces have been a lot of effort and research, these aerodynamic surface flow separation and delay as long as possible to keep the local streams attached to the blade 10. 例如,国际专利公布No. WO 2007/140771和欧洲专利申请No. EP 1944505公开了具有涡流发生器的风力涡轮机叶片。 For example, International Patent Publication No. WO 2007/140771 and European Patent Application No. EP 1944505 discloses a wind turbine blade having vortex generators. 然而,这种涡流发生器或会减少以其它方式可从风中俘获的能量。 However, this will reduce the vortex generators or otherwise may capture energy from the wind.

发明内容 DISCLOSURE

[0007] 与这些常规方式相关的这些和其它方面在此通过在多种实施例中提供风力涡轮机叶片而予以解决,该风力涡轮机叶片包括多个边界层翅片,这些边界层翅片大致平行于叶片上的流动方向对准,以便减小边界层与叶片的分离。 [0007] These conventional manner associated with these and other aspects of this that it be adopted in various embodiments provide a wind turbine blade resolved, the wind turbine blade includes a plurality of fins boundary layer, which is substantially parallel to the boundary layer fin the flow direction of the blade is aligned so as to reduce boundary layer separation and the blade.

附图说明 Brief Description

[0008] 现在将参照以下附图(图)来描述该技术的各个方面,附图不必按比例绘制,但使用了相同的参考标号来表示全部各个视图中的对应零件。 [0008] Referring now to the accompanying drawings (FIG) to describe the various aspects of this technology, the drawings are not necessarily drawn to scale, but use the same reference numerals to represent all corresponding parts in the various views.

[0009] 图1为常规风力涡轮机的示意性侧视图。 [0009] FIG. 1 is a conventional wind turbine schematic side view.

[0010] 图2为风力涡轮机叶片的顶视图。 [0010] FIG. 2 is a top view of a wind turbine blade.

[0011] 图3为沿图2中的截面线III-III所截取的截面视图。 [0011] FIG. 3 is a cross-sectional view taken along line III-III 2 are taken.

[0012] 图4为图3中所示的边界层翅片的放大侧视图。 [0012] FIG. 4 is an enlarged side view of the boundary layer of the fin shown in Figure 3.

[0013] 图5为图2中所示的风力涡轮机叶片表面的放大局部正视图。 [0013] FIG. 5 is shown in FIG. 2 an enlarged partial surface of a wind turbine blade front view.

[0014] 图6为结合图2中所示的风力涡轮机叶片使用的边界层翅片的放大局部正视图。 [0014] FIG. 6 is a combination of wind turbine blade shown in FIG. 2 for topical use enlarged front view of the fin boundary layer.

[0015] 图7为结合图2中所示的风力涡轮机叶片使用的边界层翅片的侧视图。 [0015] FIG. 7 is a combination of wind turbine blade shown in Figure 2 a side view of the use of the boundary layer fin.

[0016] 图8为结合图2中所示的风力涡轮机叶片使用的另一边界层翅片的侧视图。 [0016] Figure 8 is another combination fin boundary layer wind turbine blade shown in Figure 2 uses a side view.

[0017] 图9为压力系数相对于叶片截面无因次翼弦的曲线图。 [0017] FIG. 9 is a cross-sectional pressure coefficient with respect to the blade chord dimensionless graph.

[0018] 图10为正交于叶片表面的边界层轮廓位置相对于速度的曲线图。 [0018] FIG. 10 is perpendicular to the blade surface boundary layer profile position relative to the speed graph.

[0019] 图11为正交于叶片表面的位置相对于紊流动能的曲线图。 [0019] FIG. 11 is orthogonal to the position of the blade relative to the surface of the turbulent kinetic energy of the graph.

具体实施方式 DETAILED DESCRIPTION

[0020] 图2为结合图1中所示的风力涡轮机2或任何其它风力涡轮机使用的具有多个边界层翅片22的风力涡轮机叶片20的一个实施例的顶视图。 [0020] Figure 2 is a combination of the wind turbine 1 shown in top plan view having a plurality of fins boundary layer wind turbine blade 22 of an embodiment 2 of 20, or any other use of the wind turbine. 例如,叶片20可替换叶片10 中的任何一个,或叶片10可更改成包括叶片20的一些或所有特征。 For example, the blade 20 can be replaced with any of the blade 10, or blade 10 can be changed to include some or all of the features of the blades 20. 各所示边界层翅片22 均沿翼弦方向延伸,大致平行于叶片压力侧上的流动方向,以便减小边界层与叶片的分离。 Each fin 22 are shown in the boundary layer along the chordwise extending substantially parallel to the flow direction of the blade on the pressure side, in order to reduce boundary layer separation and the blade. 然而,一些边界层翅片22还可布置成相对于叶片上和/或叶片的相对压力侧上的流动成一定角度。 However, some of the fins 22 may also be arranged in the boundary layer with respect to the flow on the pressure side opposite the blade and / or blade on an angle.

[0021] 边界层翅片22的各个方面可关于风力涡轮机叶片的一定特征进行安置,这些特征包括叶片的翼展(跨距)长度、边界层翅片布置于其上的对应翼弦,和/或边界层翅片布置位置上的局部边界层厚度。 [0021] The various aspects of the boundary layer on the fins 22 may be certain characteristics of the wind turbine blades for resettlement, these features include the blade span (span) length, corresponding to the boundary chord fins disposed thereon and / or local boundary layer thickness boundary layer fin arrangement position. 优选的是,局部边界层厚度在叶片20或对应的风力涡轮机4 在没有边界层翅片22的情况下且以其"额定转速(rmp)“工作时来计算,其中,“额定转速"在叶片20于其根部端固定的情况下通常为每分钟大约十五至二十圈。 Preferably, the local boundary layer thickness and its 4 "rated speed (rmp)" to calculate the work of the blade 20 corresponding to the wind turbine or in the absence of the fins 22 of the boundary layer, where "rated speed" of the blade 20 on its root end fixed usually from about fifteen to twenty cycles per minute. 对于典型叶片20而言,正如可从通用电气公司获得的大约48. 7米长的叶片,在叶片20以额定转速工作的情况下所计算出的局部边界层厚度将在叶片上沿翼弦方向和翼展方向从大约1毫米变化至大约202毫米。 For the purposes of a typical blade 20, about 48.7 m long blades, as available from General Electric Company, in the case of blade 20 at the rated speed of the calculated work of local boundary layer thickness along the chord direction of the blade and span direction change from about 1 mm to about 202 mm. 在距该叶片20吸入侧前缘的60%翼弦处,边界层厚度通常在大约6毫米至52毫米之间。 Away from the suction side of the leading edge 20 of blade 60% chord point, the boundary layer thickness is typically between about 6-52 mm. 在与翼展吸入侧外部33%大致相同的翼弦位置处,边界层厚度范围可从大约6毫米变化至大约16毫米。 Chord at a position outside the suction side of the span roughly the same 33%, the boundary layer thickness may range from about 6 mm to about 16 mm change.

[0022] 边界层翅片22可沿叶片20的整个翼展布置,或仅布置在翼展的一部分上,如预计将出现边界层分离的位置。 [0022] The boundary layer along the blade fins 22 may span the entire arrangement 20, or only a portion disposed on the span, such as the position of the boundary layer separation is expected to appear. 例如,边界层翅片22可布置在叶片22翼展的外部10%至100% 上,翼展的外部25%至95%上,或翼展的外部50%至90%上。 For example, the boundary layer fins 22 may be disposed on the outer 10-100% blade span of 22, on the outer 25-95% span or on external wingspan of 50-90%. 一个或多个边界层翅片22 或成对的边界层翅片还可提供在沿叶片22翼展的分立位置处,在此位置,边界层分离有问题或可能变得有问题。 One or more pairs of the boundary layer boundary fins or fin 22 may also be provided at discrete locations along the span of the blade 22, in this position, boundary layer separation becomes a problem or potential problem.

[0023] 这里所示的边界层翅片22沿布置了对应边界层翅片的翼弦延伸。 [0023] The boundary layer fin 22 shown here corresponds to the boundary layer are arranged along a chord extending fins. 如图3中所示, 边界层翅片22的前缘可从叶片20的前缘和后缘移位。 As shown in FIG. 3, the leading edge 22 of the fin boundary layer can be shifted from the leading edge and the trailing edge 20 of the blade. 例如,边界层翅片22的前缘可从叶片20前缘移位翼弦的10%至95%之间,移位翼弦的15%至90%之间,或移位布置了边界层翅片的对应翼弦的50%至90%之间。 For example, between 10-95% fin leading edge of the boundary layer 22 may be shifted from the blade leading edge chord 20, between 15-90% shift chord, or shift the layout of the boundary layer wing sheet corresponding chord between 50-90%. 各边界层翅片22或成对的边界层翅片22的前缘和/或后缘不必彼此对准,且边界层翅片22还可具有不同或相同的长度。 Each boundary paired fins 22 or fin leading edge boundary 22 and / or the trailing edge need not aligned with each other, and the fins 22 may also have a different boundary or the same length. 例如,成对的和/或其它成组的边界层翅片22可具有或不具有相对于叶片20的前缘和后缘大致相同的位置。 For example, paired, and / or other groups of the boundary layer fin 22 may or may not have with respect to the leading and trailing edge of the blade 20 is substantially the same position.

[0024] 转到图4,边界层翅片22的高度〃 H"、长度〃 L"和/或顶面曲率半径〃 R"沿叶片20的翼展可为变化的。例如,高度"H"可为对应边界层翅片22处的局部边界层厚度的大约25%至100%之间,或50%至75%之间。长度〃 L"可为高度〃 H"的2至40倍, 或为局部边界层厚度的大致2至10倍,或为局部边界厚度的大约1至4倍。 [0024] Turning to Figure 4, the boundary layer of the fin height H 22 〃 "〃 length L" and / or the top surface of the radius of curvature 〃 R "along the blade span 20 may be varied. For example, the height of the" H " may correspond to the boundary layer fin 22 of the local boundary layer thickness of between about 25 to 100%, or between 50-75%. 〃 length L "may 〃 height H" is 2 to 40 times, or It is generally 2 to 10 times the local boundary layer thickness, or about 1-4 times the thickness of the local boundary.

[0025] 曲率半径"R"可大致恒定,或在长度"L"上变化。 [0025] the radius of curvature "R" may be substantially constant, or length "L" on the changes. 在各种实施例中,曲率半径可为高度"H"的大约2至60倍,或为局部边界层厚度的大约2至15倍。 In various embodiments, the radius of curvature for the height "H" of about 2 to 60 fold, or from about 2 to 15 times the local boundary layer thickness. 例如,曲率半径可从大约20毫米变化到300毫米,或从大约40毫米变化到大约150毫米,或从大约60毫米变化到100毫米。 For example, the radius of curvature can vary from about 20 millimeters to 300 millimeters, or from about 40 millimeters to about 150 millimeters changes, or changes from about 60 mm to 100 mm. 图7和图8示出了一些或所有边界层翅片22的顶面的各种其它的可能构造。 Figures 7 and 8 show some or all of the various other possible boundary layer fin structure 22 of the top surface.

[0026] 转到图5,示出了两对边界层翅片22,该边界层翅片22的厚度"t"可为对应边界层翅片22高度〃 H"的大约10%至100%,或大约25%至75%。作为备选,如图6中所示, 一些或所有边界层翅片22的厚度可显著更大,以便在一些或所有叶片20上形成沿翼展方向的突出部(bump)。成对或更大组合的两个边界层翅片之间的距离"d"可为高度"H" 的大约2至32倍,或4至16倍,或为局部边界层厚度的大约2至8倍。类似的是,成对或其它组合的边界层翅片之间的距离"D"还可为高度"H"的大约2至32倍,或4至16倍, 或局部边界层厚度的大约2至8倍。作为备选,如图6中所示,独立的边界层翅片22和/ 或成组的边界层翅片22之间的距离可大致为零。 [0026] Turning to Figure 5, shows the two fins 22 of the boundary layer, the thickness of the boundary layer fin 22 "t" for the corresponding boundary layer height of the fins 22 〃 H "of about 10-100%, or about 25-75%. As an alternative, as shown in Figure 6, some or all of the boundary layer thickness of the fins 22 may be significantly larger so as to form spanwise protrusion on some or all of the blades 20 (bump). from a combination of two or more pairs of the boundary layer between fins "d" may be a height "H" of about 2 to 32 times, or 4-16 times, or to the local boundary layer thickness about 2-8 times. Similarly, the distance between the fins in pairs or other combinations of the boundary between "D" may also be a height "H" of about 2 to 32 times, or 4-16 times, or local boundary about 2-8 times the thickness. Alternatively, as shown in Figure 6, separate from the boundary layer fins 22 and / or groups of the boundary layer between the fins 22 may be substantially zero.

[0027] 图9至图11示出了上文所述的叶片的一部分在具有和没有以九度冲角工作的在图5中示为22的边界层翅片的情况下的流动模拟比较结果。 [0027] FIG. 9 to 11 shows a portion of the blade above the flow simulations with and compare to nine degrees angle of attack does not work as shown in Figure 5, the boundary layer in the case where the fins 22 results . 边界层翅片22的前缘布置在距叶片22前缘的60%的翼弦处,高度"H"为局部边界层厚度的50%,长度"L〃为局部边界层厚度的五倍,顶面曲率半径"R"为60毫米,成对的两个边界层翅片之间的距离"d"为9. 33毫米,以及两对边界层翅片之间的距离"D"为16. 56毫米。 Fin leading edge of the boundary layer 22 is disposed in the leading edge of the blade 22 from the 60% chord at the height of the "H" is 50% of the local boundary layer thickness, length "L〃 five times for the local boundary layer thickness, top the radius of curvature "R" is 60 mm, the distance between the paired fins of the two boundary layer "d" is 9.33 mm, and the distance between the boundary layer between the fins of the "D" for the 16.56 mm.

[0028] 图9示出了压力系数"Cp"相对于无因次翼弦"x/c",其中,曲线30针相对于没有边界层翅片的基准情况,而曲线40针对以上段落中描述的边界层翅片22。 [0028] FIG. 9 shows a pressure coefficient "Cp" with respect to the non-dimensional chord "x / c", wherein the needle with respect to the curve 30 without fins reference boundary conditions, and curve 40 for a description of the above paragraphs The boundary layer fin 22. 图9示出了叶片20后缘附近的外侧区域50中的边界层翅片所提供的改善的压力恢复。 Figure 9 shows the outer region of the pressure of the blade near the trailing edge 20 of the fin 50 provided in the boundary layer to improve recovery. 图9还示出了叶片20前缘区域52中的增加负载。 Figure 9 also shows the leading edge of the blade 20 in the region 52 to increase the load.

[0029] 图10示出了正交于叶片吸入表面单位为米的距离〃 N"相对于单位为米每秒的局部流动速度"V",其中,曲线30针对没有边界层翅片的基准情况,而曲线40针对上文所述的边界层翅片22。图10示出了距叶片20吸入表面大约0. 02至0. 06米的区域54中减小的边界层厚度。图11示出了正交于叶片吸入表面单位为米的距离"N"相对于单位为平方米每秒的平方(m2/s2)的局部紊流动能"TKE",其中,曲线30针对没有边界层翅片的基准情况,而曲线40针对上文所述的边界层翅片22。图11示出了距叶片20吸入表面大约0. 01至0. 03米的区域56中减小的紊流动能。涡旋消散程度同样地下降。 [0029] FIG. 10 illustrates a surface perpendicular to the blade suction units of meters 〃 N "relative to the local flow velocity in meters per second" V ", in which there is no boundary curve 30 for fin base case , and curve 40 for the boundary layer above the fins 22. Figure 10 shows a blade 20 from the suction surface of approximately 0.02 to 0.06 m in the region 54 of reduced boundary layer thickness. FIG. 11 shows orthogonal to the suction surface of the blade units of meters "N" with respect to the units of square meters per second squared (m2 / s2) local turbulence kinetic energy "TKE", where there is no boundary curve for the fin 30 base case, while the curve 40 for the boundary layer above the fins 22. Figure 11 shows a blade 20 from the suction surface of approximately from 0.01 to 0.03 m in the region 56 of reduced turbulent kinetic energy. vortex Similarly extent dissipated decreased.

[0030] 这里公开的技术提供了优于常规方式的各种优点。 [0030] The techniques disclosed herein provide various advantages over conventional manner. 例如,增加边界层翅片22导致边界层厚度减小和边界层分离最低限度地减少。 For example, increasing the lead to boundary layer thickness of the boundary layer fin 22 is reduced and the reduction of boundary layer separation minimally. 随着紊流动能和紊流涡旋消散程度的降低,克服了相反的压力梯度。 With the dissipation of turbulent kinetic energy and turbulent eddies reduced extent, overcomes the opposing pressure gradient. 由于引入流入边界层区域中的自由流为流动赋能且因此减小边界层厚度,故并未显著改变空气动力性能。 Since the introduction of the inflow boundary layer region forming the free flow of liquidity and thus reduce the boundary layer thickness, it did not significantly alter the aerodynamic performance. 层流区域的显著增大导致了升力的增大和阻力的减小。 Laminar flow area increases significantly increase leading to a reduction of lift and drag. 还存在边界层厚度和紊流动能的显著减小,这会降低因其它较弱的边界层分离而造成的噪音。 There are turbulent boundary layer thickness and a significant reduction of kinetic energy, which will reduce the noise due to other weak boundary layer separation caused.

[0031] 应当强调的是,上述实施例且尤其是任何"优选"实施例,仅为在此已阐述的各种实施方式的实例,用以提供对本技术的各个方面的清楚理解。 [0031] It should be emphasized that the embodiments described above and particularly any "preferred" embodiments, are merely examples have been set forth herein in the various embodiments, various aspects of the present to provide a clear understanding of the art. 本领域的普通技术人员将能够在基本上不脱离仅由所附权利要求的适合构造所限定的保护范围的情况下改变这些实施例中的一些。 Under ordinary skill in the art without departing from the scope of protection will be able to only by the appended claims as defined for structure in the case of substantially changing some of these embodiments.

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Classifications
International ClassificationF03D1/06
Cooperative ClassificationF05B2240/30, F03D1/065, F03D1/0641, Y02E10/721, F03D1/06
European ClassificationF03D1/06C, F03D1/06, F03D1/06B6B
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